Pratt-Whitney Canada Corp

Lena Raykowski

David Denis

Czeslaw Wojtyczka

Milica Kojovic

Philippe Bonniere

Oleg Korshikov

Dave Beamish

Jean Thomassin

Jason Herborth

Ahmed Abdelrahman

Gilles Begin

Harvey Smailys

Jason Todd Herborth

A method for tuning a vibration response of an aircraft system is disclosed, where the aircraft system comprises an airframe and at least one engine dynamically coupled, the at least one engine having an engine rotor including a nose cone. The method comprises obtaining a range of frequencies associated with at least one resonance mode of the aircraft system and adding mass within the nose cone to offset at least one dominant excitation frequency of the turbofan engine outside the range of frequencies associated with the at least one resonance mode of the aircraft system. A method of tuning dynamic coupling of an aircraft system comprising an airframe and an engine mounted thereto is also disclosed.

Fan nose cone and dynamic tuning of aircrafts

A bearing arrangement rotatably supports a shaft of an aircraft engine. The bearing arrangement comprises a bearing having rolling elements disposed between inner and outer races. The inner race is affixed to the shaft. A decoupler normally structurally couples the outer race of the bearing to a stator structure of the engine. The decoupler is configured to release the bearing from the stator structure when subject to a predetermined critical load. A bumper is mounted to the stator structure and encircles the bearing. The bumper has a radially inwardly facing surface disposed in close proximity to a radially outer surface of the outer race of the bearing and defines therewith a radial gap to accommodate and constrain an orbiting motion of the rotor about the central axis of the engine after decoupling at the bearing. The bumper further has an axially forwardly facing surface which is axially spaced by a predetermined axial fore gap from a first flange projecting radially outwardly from a front end portion of the outer race of the bearing. The first flange of the outer race is axially trapped between the stator structure and the bumper. After decoupling, the bearing is free to axially and radially move within the radial gap and the axial fore gap.

Post FBO windmilling bumper

A double frangible bearing support structure supports a low pressure rotor of an aircraft engine. The support structure has a first bearing assembly including a first bearing supported by a first bearing support adapted to buckle or frange when subject to a predetermined critical load resulting from an abnormal rotor imbalance. The support structure has a second bearing assembly comprising a second bearing having rolling elements disposed between inner and outer races. The outer race is connected to a second bearing support by means of frangible bolts adapted to fail when subject to a predetermined critical load resulting from radial displacements and loads of the low pressure rotor following decoupling/franging at the first bearing support.

Double frangible bearing support

A bearing support ring includes a plurality of contact pads radially protruding from inner and outer circumferential surfaces of the ring. Flexible portions of the ring are defined between the contact pads and have a radial thickness less than that of the ring at the contact pads, such as to permit elastic deflection of the ring in a radial direction between the contact pads. Openings sized to permit unrestricted oil flow are provided, such as within the flexible portions of the ring.

Bearing support flexible ring

Growing community of inventors

Mississauga, Canada

Lena Raykowski